Rotatable wing tip joint and method of making same

ABSTRACT

A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least one actuator. A first end of each at least one actuator is coupled to the linking member, and a second end of each at least one actuator is coupleable to one of the wing base and the wing tip. The at least one actuator is operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base.

BACKGROUND

The field of the disclosure relates generally to rotatable wing tipjoints, and, more particularly, to systems and methods for rotating awing tip while maintaining an aerodynamic wing surface.

At least some known aircraft include wings with rotatable wing tips.Such rotatable wing tips may be utilized, for example, as astabilization and/or control surface of the aircraft. Such rotatablewing tips typically rotate relative to a wing base about a hingemechanism.

At least some known hinge mechanisms are at least partially exposed tosurrounding air flow when the wing tip is rotated. However, such anexposed hinge mechanism tends to create adverse aerodynamic effects.Such aerodynamic effects may be exacerbated under certain flightconditions, such as, for example, when the aircraft operates atsupersonic speeds. Alternatively, at least some known wings withrotatable wing tips include a flexible skin that extends between thewing base and the wing tip, such that it covers the hinge mechanism whenthe wing tip is rotated. However, the flexible skin tends to crease andwrinkle around the hinge mechanism when the wing tip is rotated, whichtends to create adverse aerodynamic effects such as, for example, whenthe aircraft operates at supersonic speeds.

BRIEF DESCRIPTION

In one aspect, a joint for coupling a wing tip to a wing base isprovided. The joint includes a linking member that extends from a firstend to a second end. The linking member first end is coupleable to thewing base, and the linking member second end is coupleable to the wingtip. The linking member defines a first hinge line and a second hingeline, and the first hinge line and said second hinge line aresubstantially parallel. The joint also includes at least one actuator. Afirst end of each at least one actuator is coupled to the linkingmember, and a second end of each at least one actuator is coupleable toone of the wing base and the wing tip. The at least one actuator isoperable to rotate the wing tip about the first and second hinge linesbetween a first orientation and a second orientation relative to thewing base.

In another aspect, an aircraft is provided. The aircraft includes atleast one wing that has a wing base and a wing tip. The aircraft alsoincludes a linking member that extends from a first end to a second end.The linking member first end is coupled to the wing base, and thelinking member second end is coupled to the wing tip. The linking memberdefines a first hinge line and a second hinge line, and the first hingeline and the second hinge line are substantially parallel. The aircraftfurther includes at least one actuator. A first end of each at least oneactuator is coupled to the linking member, and a second end of each atleast one actuator is coupled to one of the wing base and the wing tip.The at least one actuator is operable to rotate the wing tip about thefirst and second hinge lines between a first orientation and a secondorientation relative to the wing base.

In another aspect, a method of coupling a wing base and a wing tip isprovided. The method includes coupling a first end of a linking memberto the wing base and coupling a second end of the linking member to thewing tip. The linking member defines a first hinge line and a secondhinge line, and the first hinge line and the second hinge line aresubstantially parallel. The method also includes coupling a first end ofat least one actuator to the linking member, and coupling a second endof each at least one actuator to one of the wing base and the wing tip.The at least one actuator is operable to rotate the wing tip about thefirst and second hinge lines between a first orientation and a secondorientation relative to the wing base.

The features, functions, and advantages that have been discussed can beachieved independently in various embodiments or may be combined in yetother embodiments further details of which can be seen with reference tothe following description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic diagram of an exemplary aircraft;

FIG. 2 is a schematic cross-sectional side view of a first embodiment ofa wing tip joint that may be used with the aircraft shown in FIG. 1,with a wing tip in a first orientation;

FIG. 3 is a schematic cross-sectional side view of the first embodimentof the wing tip joint shown in FIG. 2, with the wing tip in a secondorientation;

FIG. 4 is a schematic cross-sectional top view of the first embodimentof the wing tip joint shown in FIG. 2, with the wing tip in the firstorientation;

FIG. 5 is a schematic cross-sectional side view of a second embodimentof the wing tip joint that may be used with the aircraft shown in FIG.1, with the wing tip in the first orientation;

FIG. 6 is a schematic cross-sectional side view of the second embodimentof the wing tip joint shown in FIG. 5, with the wing tip in the secondorientation;

FIG. 7 is a schematic cross-sectional top view of the second embodimentof the wing tip joint shown in FIG. 5, with the wing tip in the firstorientation;

FIG. 8 is a schematic cross-sectional side view of a third embodiment ofthe wing tip joint that may be used with the aircraft shown in FIG. 1,with the wing tip in the first orientation;

FIG. 9 is a schematic cross-sectional side view of the third embodimentof the wing tip joint shown in FIG. 8, with the wing tip in the secondorientation;

FIG. 10 is a schematic cross-sectional top view of the third embodimentof the wing tip joint shown in FIG. 8, with the wing tip in the firstorientation; and

FIG. 11 is a flowchart of an embodiment of a method of coupling a wingtip and a wing base, such as the wing tip and wing base shown in FIGS.1-10.

DETAILED DESCRIPTION

Embodiments of the wing tip joint and method described herein providefor rotation of a wing tip relative to a wing base with reduced oreliminated adverse aerodynamic effect. The embodiments provide forrotation of the wing tip about two offset, substantially parallel hingelines, rather than about a single axis. As such, when the wing tip is ina rotated state, a relatively large radius of curvature is imparted to aflexible skin that extends between the wing base and the wing tip. Therelatively large radius of curvature reduces or eliminates creases andwrinkles in the flexible skin near the hinge lines, as compared to asimilar amount of rotation at a single-hinged joint.

Referring more particularly to the drawings, implementations of thedisclosure may be described in the context of an aircraft 10 shownschematically in FIG. 1. Aircraft 10 includes at least one wing 12 thatextends from a fuselage 14. The at least one wing 12 includes a wingbase 16 that extends from a first end 18 to an opposing second end 20.Wing base first end 18 is coupled to fuselage 14.

The at least one wing 12 also includes a wing tip 22 that extends from afirst end 24 to an opposing second end 26. Wing tip 22 is coupled towing base 16 at a wing tip joint 100. More specifically, wing tip firstend 24 is coupled to wing base second end 20 at wing tip joint 100, suchthat wing tip 22 is rotatable with respect to wing base 16. In theillustrated embodiment, wing tip 22 is rotatable with respect to wingbase 16 about an axis generally parallel to a longitudinal axis 30 offuselage 14. In alternative embodiments, wing tip 22 is rotatable withrespect to wing base 16 about an axis that is not generally parallel tolongitudinal axis 30.

FIG. 2 and FIG. 3 are schematic side cross-sectional views, and FIG. 4is a schematic cross-sectional top view, of a first embodiment of wingtip joint 100, designated as wing tip joint 200, that may be used with,for example, aircraft 10. In FIG. 2 and FIG. 4, wing tip 22 isillustrated in a first orientation 102 relative to wing base 16. In FIG.3, wing tip 22 is illustrated in a second orientation 104 relative towing base 16. A flexible outer skin 60 of the at least one wing 12extends over at least a portion of joint 200 between wing base 16 andwing tip 22.

With reference to FIGS. 2-4, in the illustrated embodiment, firstorientation 102 is a neutral orientation, such that a spanwise axis 108of wing tip 22 is substantially parallel to a spanwise axis 106 of wingbase 16. In alternative embodiments, first orientation 102 is other thana neutral orientation, such that spanwise axis 108 of wing tip 22 is notsubstantially parallel to spanwise axis 106 of wing base 16.

In second orientation 104, wing tip 22 is rotated by an angle 110relative to first orientation 102. Angle 110 is defined about an axis112 that generally lies within a plane defined by wing 12. In certainembodiments, axis 112 is substantially parallel to a line drawn from anypoint on a leading edge 32 of the at least one wing 12 to any point on atrailing edge 34 of the at least one wing 12. In the illustratedembodiment, axis 112 is substantially parallel to longitudinal axis 30(which extends out of the page in the view shown in FIGS. 2 and 3).

In certain embodiments of joint 100, such as joint 200, wing tip 22 isconfigured to rotate from first orientation 102 in a generally downwarddirection towards second orientation 104. For example, in theillustrated embodiment, wing tip 22 is configured to rotate generallytowards the ground from first orientation 102 to second orientation 104when aircraft 10 (shown in FIG. 1) is in a typical operating condition.In alternative embodiments, wing tip 22 is configured to rotate fromfirst orientation 102 in a generally upward direction towards secondorientation 104.

In certain embodiments of joint 100, such as joint 200, wing tip 22 isrotatable to a maximum angle 110 that facilitates improved control ofaircraft 10 (shown in FIG. 1) in a selected operating condition, suchas, but not limited to, a supersonic operating condition. For example,in some embodiments, wing tip 22 is rotatable to a maximum angle 110 ina range of from about 10 degrees to about 65 degrees. Moreover, incertain embodiments, wing tip 22 is rotatable to a maximum angle 110 ina range of from about 40 degrees to about 55 degrees. In a particularembodiment, wing tip 22 is rotatable to a maximum angle 110 of about 50degrees.

Embodiments of joint 100, such as joint 200, enable wing tip 22 to movebetween first orientation 102 and second orientation 104 other than by asimple rotation about a single axis, such as axis 112. For example, inthe illustrated embodiment, joint 200 includes a linking member 202.Linking member 202 extends from a first end 204 to a second end 206.Linking member first end 204 is configured to be coupled to wing base16, and linking member second end 206 is configured to be coupled towing tip 22. More specifically, in the illustrated embodiment, linkingmember first end 204 is rotatably coupled to a rib 40 of wing base 16,and linking member second end 206 is rotatably coupled to a rib 42 ofwing tip 22. The rotatable coupling of linking member first end 204 towing base 16 defines a first hinge line 210, and the rotatable couplingof linking member second end 206 to wing tip 22 defines a second hingeline 212.

First hinge line 210 and second hinge line 212 are substantiallyparallel and offset from each other by a distance 270. In particular,first hinge line 210 and second hinge line 212 each are substantiallyparallel to axis 112. In an embodiment, first hinge line 210 is a firstpin joint 214 that rotatably couples linking member first end 204 towing base 16, and second hinge line 212 is a second pin joint 216 thatrotatably couples linking member second end 206 to wing tip 22. Inalternative embodiments, first hinge line 210 and second hinge line 212each are defined by any suitable coupling between linking member 202 andwing base 16 and wing tip 22, respectively, that enables joint 200 tofunction as described herein.

Joint 200 further includes a first actuator 220 and a second actuator230 that are operable to rotate wing tip 22 about first hinge line 210and second hinge line 212 between first orientation 102 and secondorientation 104. First actuator 220 includes a first end 222, and asecond end 224 that is linearly extendable relative to first end 222.The extension of second end 224 relative to first end 222 iscontrollable, such as by a suitable control system (not shown) ofaircraft 10 (shown in FIG. 1). Similarly, second actuator 230 includes afirst end 232 and a second end 234 that is linearly extendable relativeto first end 232, and the extension of second end 234 relative to firstend 232 is controllable.

In an embodiment, each of first actuator 220 and second actuator 230 arehydraulic actuators. In another embodiment, at least one of firstactuator 220 and second actuator 230 is a pneumatic actuator. In anotherembodiment, at least one of first actuator 220 and second actuator 230is an electric actuator. In alternative embodiments, each of firstactuator 220 and second actuator 230 is any suitable actuator thatenables joint 200 to function as described herein.

In FIG. 2, first actuator 220 is illustrated in a first state 226wherein first actuator second end 224 is at a first position relative tofirst actuator first end 222, and second actuator 230 is illustrated ina first state 236 wherein second actuator second end 234 is at a firstposition relative to second actuator first end 232. In FIG. 3, firstactuator 224 is illustrated in a second state 228 wherein first actuatorsecond end 224 is at a second position relative to first actuator firstend 222, and second actuator second end 234 is illustrated in a secondstate 238 wherein second actuator second end 234 is at a second positionrelative to second actuator first end 232. In the illustratedembodiment, actuators 220 and 230 in respective second states 228 and238 have respective second ends 224 and 234 that are extended relativeto respective first states 226 and 236.

First actuator first end 222 is coupled, at least indirectly, to linkingmember 202. More specifically, in the illustrated embodiment, firstactuator first end 222 is rotatably coupled to wing base 16 at firsthinge line 210, such that first actuator first end 222 is at leastindirectly coupled to linking member 202 through first hinge line 210.In the illustrated embodiment, first actuator first end 222 is coupledto rib 40 at first pin joint 214. In an alternative embodiment, firstactuator first end 222 is coupled to wing base 16 at a separate pinjoint (not shown) that has an axis of rotation substantially parallel tofirst pin joint 214. In other alternative embodiments, first actuatorfirst end 222 is coupled to linking member 202 by any suitable couplingthat enables joint 200 to function as described herein. Additionally,first actuator second end 224 is coupled to wing tip 22. In theillustrated embodiment, first actuator second end 224 is rotatablycoupled to rib 42 at a third pin joint 240. In other alternativeembodiments, first actuator second end 224 is coupled to wing tip 22 byany suitable coupling that enables joint 200 to function as describedherein.

Second actuator first end 232 is coupled, at least indirectly, tolinking member 202. More specifically, in the illustrated embodiment,second actuator first end 232 is rotatably coupled to wing tip 22 atsecond hinge line 212, such that second actuator first end 232 is atleast indirectly coupled to linking member 202 through second hinge line212. In the illustrated embodiment, second actuator first end 232 iscoupled to rib 42 at second pin joint 216. In an alternative embodiment,second actuator first end 232 is coupled to wing tip 22 at a separatepin joint (not shown) that has an axis of rotation substantiallyparallel to second pin joint 216. In other alternative embodiments,second actuator first end 232 is coupled to linking member 202 by anysuitable coupling that enables joint 200 to function as describedherein. Additionally, second actuator second end 234 is coupled to wingbase 16. In the illustrated embodiment, second actuator second end 234is rotatably coupled to rib 40 at a fourth pin joint 242. In otheralternative embodiments, second actuator second end 234 is coupled towing base 16 by any suitable coupling that enables joint 200 to functionas described herein.

As illustrated in FIG. 2, first actuator 220 and second actuator 230 areconfigured to orient wing tip 22 in first orientation 102 when firstactuator 220 and second actuator 230 are in respective first states 226and 236. As illustrated in FIG. 3, first actuator 220 and secondactuator 230 are configured to orient wing tip 22 in second orientation104 when first actuator 220 and second actuator 230 are in respectivesecond states 228 and 238. Moreover, first actuator 220 and secondactuator 230 cooperate with linking member 202 such that secondorientation 104 defines a complex rotation from first orientation 102about first hinge line 210 and second hinge line 212, rather than asimple rotation about a single axis, such as axis 112. For example, inan embodiment, angle 110 is about 50 degrees, and wing tip 22 in secondorientation 104 is rotated about 25 degrees about first hinge line 210and about 25 degrees about second hinge line 212 from first orientation102. It should be understood that an inner radius of curvature 262 ofjoint 100, 200 is increased relative to an inner radius of curvature(not shown) that would occur for a similar joint having a simplerotation about a single axis. As a result, a portion of flexible outerskin 60 defined by inner radius 262 is substantially smooth when wingtip 22 is moved between first orientation 102 and second orientation104. For example, the portion of flexible outer skin 60 defined by innerradius 262 exhibits reduced or no creasing or folding when wing tip 22is moved between first orientation 102 and second orientation 104.

Linking member 202 includes a surface 280 defined proximate the portionof flexible outer skin 60 defined by inner radius 262. In certainembodiments, surface 280 has a shape between first end 204 and secondend 206 that enables joint 200 to position wing tip 22 in secondorientation 104 without interference between linking member 202 and theportion of flexible outer skin 60 defined by inner radius 262. Forexample, in the illustrated embodiment, surface 280 has a curvaturebetween first end 204 and second end 206 that substantially correspondsto inner radius of curvature 262. In an alternative embodiment, thecurvature of surface 280 is greater than inner radius of curvature 262.In another alternative embodiment, surface 280 is substantially linearbetween first end 204 and second end 206, and at least one of firsthinge line 210 and second hinge line 212 is offset towards therespective one of fourth pin joint 242 and third pin joint 240sufficiently to enable joint 200 to position wing tip 22 in secondorientation 104 without interference between linking member 202 and theportion of flexible outer skin 60 defined by inner radius 262. In otheralternative embodiments, surface 280 has any other shape andconfiguration that enables joint 200 to function as described herein.

FIG. 5 and FIG. 6 are schematic cross-sectional side views, and FIG. 7is a schematic cross-sectional top view, of a second embodiment of wingtip joint 100, designated as wing tip joint 300, that may be used with,for example, aircraft 10. In FIG. 5 and FIG. 7, wing tip 22 isillustrated in first orientation 102 relative to wing base 16. In FIG.6, wing tip 22 is illustrated in second orientation 104 relative to wingbase 16. With reference to FIGS. 5-7, in the illustrated embodiment,first orientation 102 again is a neutral orientation, and secondorientation 104 again has wing tip 22 rotated relative to firstorientation 102 by angle 110 about axis 112. Angle 110 and axis 112 areas described above in the context of joint 200. In addition, wing tip 22again is configured to rotate from first orientation 102 in a generallydownward direction towards second orientation 104. In alternativeembodiments, first orientation 102 is other than a neutral orientation,and/or wing tip 22 is configured to rotate from first orientation 102 ina generally upward direction towards second orientation 104. As withcertain other embodiments of joint 100, joint 300 enables wing tip 22 tomove between first orientation 102 and second orientation 104 other thanby a simple rotation about a single axis, such as axis 112.

For example, in the illustrated embodiment, joint 300 includes a linkingmember 302. Linking member 302 extends from a first end 304 to a secondend 306. Linking member first end 304 is configured to be coupled towing base 16, and linking member second end 306 is configured to becoupled to wing tip 22. More specifically, in the illustratedembodiment, linking member first end 304 is rotatably coupled to rib 40of wing base 16, and linking member second end 306 is rotatably coupledto rib 42 of wing tip 22. The rotatable coupling of linking member firstend 304 to wing base 16 defines a first hinge line 310, and therotatable coupling of linking member second end 306 to wing tip 22defines a second hinge line 312.

First hinge line 310 and second hinge line 312 are substantiallyparallel and offset from each other by a distance 371. In particular,first hinge line 310 and second hinge line 312 each are substantiallyparallel to axis 112. In an embodiment, first hinge line 310 is a firstpin joint 314 that rotatably couples linking member first end 304 towing base 16, and second hinge line 312 is a second pin joint 316 thatrotatably couples linking member second end 306 to wing tip 22. Inalternative embodiments, first hinge line 310 and second hinge line 312each are defined by any suitable coupling between linking member 302 andwing base 16 and wing tip 22, respectively, that enables joint 300 tofunction as described herein.

Joint 300 further includes a first actuator 320 and a second actuator330 that are operable to rotate wing tip 22 about first hinge line 310and second hinge line 312 between first orientation 102 and secondorientation 104. First actuator 320 includes a first end 322, and asecond end 324 that is rotatable relative to first end 322 about anactuator axis 352. In the illustrated embodiment, actuator axis 352 issubstantially parallel to axis 112. The rotation of second end 324relative to first end 322 is controllable, such as by a suitable controlsystem (not shown) of aircraft 10 (shown in FIG. 1). Similarly, secondactuator 330 includes a first end 332 and a second end 334 that isrotatable relative to first end 332 about actuator axis 352, and therotation of second end 334 relative to first end 332 is controllable.Thus, in the illustrated embodiment, first actuator 320 and secondactuator 330 are coaxially rotatable with respect to linking member 302.In alternative embodiments, each of first actuator 320 and secondactuator 330 is rotatable about a separate respective actuator axis (notshown).

In an embodiment, each of first actuator 320 and second actuator 330 arehydraulic actuators. In another embodiment, at least one of firstactuator 320 and second actuator 330 is a pneumatic actuator. In anotherembodiment, at least one of first actuator 320 and second actuator 330is an electric actuator. In alternative embodiments, each of firstactuator 320 and second actuator 330 is any suitable actuator thatenables joint 300 to function as described herein.

In FIG. 5, first actuator 320 is illustrated in a first state 326wherein first actuator second end 324 is at a first position relative tofirst actuator first end 322, and second actuator 330 is illustrated ina first state 336 wherein second actuator second end 334 is at a firstposition relative to second actuator first end 332. In FIG. 6, firstactuator 320 is illustrated in a second state 328 wherein first actuatorsecond end 324 is at a second position relative to first actuator firstend 322, and second actuator second end 334 is illustrated in a secondstate 338 wherein second actuator second end 334 is at a second positionrelative to second actuator first end 332. In the illustratedembodiment, actuators 320 and 330 in respective second states 328 and338 have respective second ends 324 and 334 that are oppositely rotatedabout actuator axis 352, away from a midline 350 of linking member 302relative to respective first states 326 and 336.

Each of first actuator first end 322 and second actuator first end 332is coupled, at least indirectly, to linking member 302. In theillustrated embodiment, each of first actuator first end 322 secondactuator first end 332 is coupled to linking member 302 for rotationabout actuator axis 352. Each of first actuator first end 322 and secondactuator first end 332 is coupled to linking member 302 by any suitablecoupling that enables joint 300 to function as described herein.

Additionally, first actuator second end 324 is coupled to wing base 16.In the illustrated embodiment, first actuator second end 324 isrotatably coupled to a first connecting member 360 at a fifth pin joint364, and first connecting member 360 is rotatably coupled to rib 40 at athird pin joint 340. In alternative embodiments, first actuator secondend 324 is coupled to wing base 16 by any suitable coupling that enablesjoint 300 to function as described herein. Similarly, second actuatorsecond end 334 is coupled to wing tip 22. In the illustrated embodiment,second actuator second end 334 is rotatably coupled to a secondconnecting member 370 at a sixth pin joint 372, and second connectingmember 370 is rotatably coupled to rib 42 at a fourth pin joint 342. Inalternative embodiments, second actuator second end 334 is coupled towing tip 22 by any suitable coupling that enables joint 300 to functionas described herein.

As illustrated in FIG. 5, first actuator 320 and second actuator 330 areconfigured to orient wing tip 22 in first orientation 102 when firstactuator 320 and second actuator 330 are in respective first states 326and 336. As illustrated in FIG. 6, first actuator 320 and secondactuator 330 are configured to orient wing tip 22 in second orientation104 when first actuator 320 and second actuator 330 are in respectivesecond states 328 and 338.

Moreover, first actuator 320 and second actuator 330 cooperate withlinking member 302 such that second orientation 104 defines a complexrotation from first orientation 102 about first hinge line 310 andsecond hinge line 312, rather than a simple rotation about a singleaxis, such as axis 112. For example, in an embodiment, angle 110 isabout 50 degrees, and wing tip 22 in second orientation 104 is rotatedabout 25 degrees about first hinge line 310 and about 25 degrees aboutsecond hinge line 312 from first orientation 102. It should beunderstood that an inner radius of curvature 362 of joint 100, 300 isincreased relative to an inner radius of curvature (not shown) thatwould occur for a similar joint having a simple rotation about a singleaxis. As a result, a portion of flexible outer skin 60 defined by innerradius 362 is substantially smooth when wing tip 22 is moved betweenfirst orientation 102 and second orientation 104. For example, theportion of flexible outer skin 60 defined by inner radius 362 exhibitsreduced or no creasing or folding when wing tip 22 is moved betweenfirst orientation 102 and second orientation 104.

Linking member 302 includes a surface 380 defined proximate the portionof flexible outer skin 60 defined by inner radius 362. In certainembodiments, surface 380 has a shape that enables joint 300 to positionwing tip 22 in second orientation 104 without interference betweenlinking member 302 and the portion of flexible outer skin 60 defined byinner radius 362. For example, in the illustrated embodiment, surface380 proximate each of first end 304 and second end 306 is curved towardsactuator axis 352. In an alternative embodiment, surface 380 issubstantially linear between first end 304 and second end 306, and atleast one of first hinge line 310 and second hinge line 312 is offsettowards the respective one of third pin joint 340 and fourth pin joint342 sufficiently to enable joint 300 to position wing tip 22 in secondorientation 104 without interference between linking member 302 and theportion of flexible outer skin 60 defined by inner radius 362. In otheralternative embodiments, surface 380 has any other shape andconfiguration that enables joint 300 to function as described herein.

FIG. 8 and FIG. 9 are schematic cross-sectional side views, and FIG. 10is a schematic cross-sectional top view, of a third embodiment of wingtip joint 100, designated as wing tip joint 400, that may be used with,for example, aircraft 10. In FIG. 8 and FIG. 10, wing tip 22 isillustrated in first orientation 102 relative to wing base 16. In FIG.9, wing tip 22 is illustrated in second orientation 104 relative to wingbase 16. With reference to FIGS. 8-10, in the illustrated embodiment,first orientation 102 again is a neutral orientation, and secondorientation 104 again has wing tip 22 rotated relative to firstorientation 102 by angle 110 about axis 112. Angle 110 and axis 112 areas described above in the context of joints 200 and 300. In addition,wing tip 22 again is configured to rotate from first orientation 102 ina generally downward direction towards second orientation 104. Inalternative embodiments, first orientation 102 is other than a neutralorientation, and/or wing tip 22 is configured to rotate from firstorientation 102 in a generally upward direction towards secondorientation 104. As with certain other embodiments of joint 100, joint400 enables wing tip 22 to move between first orientation 102 and secondorientation 104 other than by a simple rotation about a single axis,such as axis 112.

For example, in the illustrated embodiment, joint 400 includes a linkingmember 402. Linking member 402 extends from a first end 404 to a secondend 406. More specifically, in the illustrated embodiment, linkingmember first end 404 is defined on a first portion 401 of linking member402, and linking member second end 406 is defined on a second portion403 of linking member 402. Linking member first end 404 is configured tobe coupled to wing base 16, and linking member second end 406 isconfigured to be coupled to wing tip 22. More specifically, in theillustrated embodiment, linking member first portion 401 is fixedlycoupled at first end 404 to rib 40 of wing base 16, and linking membersecond portion 403 is fixedly coupled at second end 406 to rib 42 ofwing tip 22.

A first slot 405 defined in linking member first portion 401 extendsfrom a first end 407 to a second end 409. First slot 405 is configuredto receive a first pin 411 that extends from linking member secondportion 403, such that first pin 411 is constrained to move within firstslot 405. A second slot 413 defined in linking member first portion 401extends from a first end 415 to a second end 417. Second slot 413 isconfigured to receive a second pin 419 that extends from linking membersecond portion 403, such that second pin 419 is constrained to movewithin second slot 413.

A position of first pin 411 in first slot 405, and a correspondingposition of second pin 419 in second slot 413, defines a correspondingrotation of linking member second portion 403 relative to linking memberfirst portion 401. First pin 411 defines a first hinge line 410, andsecond pin 419 defines a second hinge line 412. In alternativeembodiments, at least one of first hinge line 410 and second hinge line412 is defined by any other suitable coupling between linking memberfirst portion 401 and linking member second portion 403 that enablesjoint 400 to function as described herein. First hinge line 410 andsecond hinge line 412 are substantially parallel and offset from eachother by a distance 470. In particular, first hinge line 410 and secondhinge line 412 each are substantially parallel to axis 112.

Joint 400 further includes a first actuator 420 that is operable torotate wing tip 22 about first hinge line 410 and second hinge line 412between first orientation 102 and second orientation 104. First actuator420 includes a second end 424, and a first end 422 that is linearlyextendable relative to second end 424. The extension of first end 422relative to second end 424 is controllable, such as by a suitablecontrol system (not shown) of aircraft 10 (shown in FIG. 1). In FIG. 8,first actuator 420 is illustrated in a first state 426 wherein firstactuator second end 424 is at a first position relative to firstactuator first end 422. In FIG. 9, first actuator 420 is illustrated ina second state 428 wherein first actuator second end 424 is at a secondposition relative to first actuator first end 422. In the illustratedembodiment, first actuator 420 in second state 428 has first end 422extended relative to first state 426.

First actuator first end 422 is coupled, at least indirectly, to linkingmember 402. More specifically, in the illustrated embodiment, firstactuator first end 422 is rotatably coupled to second pin 419, such thatfirst actuator first end 422 is at least indirectly coupled to linkingmember 402 through second hinge line 412. In an alternative embodiment,first actuator first end 422 is coupled to linking member 402 at aseparate pin joint (not shown) that has an axis of rotationsubstantially parallel to second pin 419. In other alternativeembodiments, first actuator first end 422 is coupled to linking member402 by any suitable coupling that enables joint 400 to function asdescribed herein. Additionally, first actuator second end 424 is coupledto one of wing base 16 and wing tip 22. In the illustrated embodiment,first actuator second end 424 is rotatably coupled to wing base 16 at athird pin joint 440. In other alternative embodiments, first actuatorsecond end 424 is coupled to one of wing base 16 and wing tip 22 by anysuitable coupling that enables joint 400 to function as describedherein.

As illustrated in FIG. 8, first actuator 420 is configured to orientwing tip 22 in first orientation 102 when first actuator 420 is in firststate 426. As illustrated in FIG. 9, first actuator 420 is configured toorient wing tip 22 in second orientation 104 when first actuator 420 isin second state 428.

Moreover, first actuator 420 cooperates with linking member 402 suchthat second orientation 104 defines a complex rotation from firstorientation 102 about first hinge line 410 and second hinge line 412,rather than a simple rotation about a single axis, such as axis 112. Forexample, in an embodiment, angle 110 is about 50 degrees, and wing tip22 in second orientation 104 is rotated about 25 degrees about firsthinge line 410 and about 25 degrees about second hinge line 412 fromfirst orientation 102. It should be understood that an inner radius ofcurvature 462 of joint 100, 400 is increased relative to an inner radiusof curvature (not shown) that would occur for a similar joint having asimple rotation about a single axis. As a result, a portion of flexibleouter skin 60 defined by inner radius 462 is substantially smooth whenwing tip 22 is moved between first orientation 102 and secondorientation 104. For example, the portion of flexible outer skin 60defined by inner radius 462 exhibits reduced or no creasing or foldingwhen wing tip 22 is moved between first orientation 102 and secondorientation 104.

Linking member 402 includes a surface 480 defined proximate the portionof flexible outer skin 60 defined by inner radius 462. In certainembodiments, surface 480 has a shape that enables joint 400 to positionwing tip 22 in second orientation 104 without interference betweenlinking member 402 and the portion of flexible outer skin 60 defined byinner radius 462. For example, in the illustrated embodiment, surface480 includes a first portion surface 481 defined on first portion 401,and a second portion surface 483 defined on second portion 403. As firstportion 401 and second portion 403 rotate relative to first and secondhinge lines 410 and 412, first portion surface 481 and second portionsurface 483 cooperate to avoid interference between linking member 402and the portion of flexible outer skin 60 defined by inner radius 462.In other alternative embodiments, surface 480 has any other shape andconfiguration that enables joint 400 to function as described herein.

FIG. 11 is a flowchart of an embodiment of a method 500 of coupling awing tip, such as wing tip 22, and a wing base, such as wing base 16.With reference to FIGS. 1-11, method 500 includes coupling 502 a firstend of a linking member, such as linking member 202, 302, or 402, to thewing base, and coupling 504 a second end of the linking member to thewing tip. The linking member defines a first hinge line, such as firsthinge line 210, 310, or 410, and a second hinge line, such as secondhinge line 212, 312, or 412. The first hinge line and the second hingeline are substantially parallel. Method 500 also includes coupling 506 afirst end of each of at least one actuator, such as first actuator 220,320, or 420 and/or second actuator 230 or 330, to the linking member.Method 500 further includes coupling 508 a second end of each at leastone actuator to one of the wing base and the wing tip. The at least oneactuator is operable to rotate the wing tip about the first and secondhinge lines between a first orientation, such as first orientation 102,and a second orientation, such as second orientation 104, relative tothe wing base.

In certain embodiments, method 500 also includes one or more additionalsteps, which are linked by dashed lines in FIG. 11. For example, incertain embodiments, method 500 includes coupling 510 the second end ofthe linking member such that the first and second hinge lines are offsetfrom each other by a distance, such as distance 270, 371, or 470. Insome embodiments, method 500 further includes coupling 512 the secondend of each at least one actuator such that the at least one actuatorcooperates with the linking member such that the second orientationdefines a rotation from the first orientation about the first and secondhinge lines. Moreover, in certain embodiments, method 500 includesextending 514 a flexible outer skin, such as flexible outer skin 60,between the wing base and the wing tip. A portion of the flexible outerskin defined by an inner radius, such as inner radius 262, 362, or 462,is substantially smooth when the wing tip is moved between the firstorientation and the second orientation.

Additionally, in certain embodiments, each at least one actuator secondend, such as first actuator second end 224 or 424 or second actuatorsecond end 234, is linearly extendable relative to the at least oneactuator first end, such as first actuator first end 222 or 422 orsecond actuator first end 232. In some such embodiments, method 500includes coupling 516 the second end of each at least one actuator suchthat each at least one actuator second end is movable to a firstposition relative to the at least one actuator first end to position thewing tip in the first orientation, and each at least one actuator secondend is movable to a second position relative to the at least oneactuator first end to position the wing tip in the second orientation.

Moreover, in certain embodiments, each at least one actuator second end,such as first actuator second end 324 or second actuator second end 334,is rotatable relative to the at least one actuator first end, such asfirst actuator first end 322 or second actuator first end 332, about anactuator axis, such as actuator axis 352. In some such embodiments,method 500 includes coupling 518 the second end of each at least oneactuator such that each at least one actuator second end is movable to afirst position relative to the at least one actuator first end toposition the wing tip in the first orientation, and each at least oneactuator second end is movable to a second position relative to the atleast one actuator first end to position the wing tip in the secondorientation.

Further, in certain embodiments, the linking member first end is definedon a first portion, such as first portion 401, of the linking member andthe linking member second end is defined on a second portion, such assecond portion 403, of the linking member. The linking member firstportion includes a first slot, such as first slot 405, and a secondslot, such as second slot 413. The linking member second portionincludes a first pin, such as first pin 411, that defines the firsthinge line, and a second pin, such as second pin 419, that defines thesecond hinge line. In some such embodiments, method 500 includescoupling 520 the linking member first portion and the linking membersecond portion such that the first pin is received in the first slot andthe second pin is received in the second slot.

Each of the processes of method 500 may be performed or carried out by asystem integrator, a third party, and/or a customer. For the purposes ofthis description, a system integrator may include without limitation anynumber of aircraft manufacturers and major-system subcontractors; athird party may include without limitation any number of venders,subcontractors, and suppliers; and a customer may be an airline, leasingcompany, military entity, service organization, and so on. Moreover,although an aerospace example is shown, the principles of the inventionmay be applied to other industries, such as the automotive industry.

The embodiments described herein provide a wing tip joint and method forcoupling a wing tip to a wing base. The embodiments provide a wing tipjoint configured to rotate the wing tip about two offset, substantiallyparallel hinge lines, rather than about a single axis. As such, aflexible skin that extends between the wing base and the wing tipmaintains a relatively large radius of curvature when the wing tip is ina rotated state.

The embodiments described herein provide improvements over at least someknown rotatable wing tips. As compared to at least some known rotatablewing tips, embodiments of the wing tip joint described herein providefor reduced or eliminated creases and wrinkles in the flexible skin nearthe hinge mechanism. The reduction or elimination of creases andwrinkles facilitates a reduced adverse aerodynamic effect proximate thehinge mechanism, and thus facilitates more efficient operation of anassociated aircraft.

This written description uses examples to disclose variousimplementations, which include the best mode, to enable any personskilled in the art to practice those implementations, including makingand using any devices or systems and performing any incorporatedmethods. The patentable scope is defined by the claims, and may includeother examples that occur to those skilled in the art. Such otherexamples are intended to be within the scope of the claims if they havestructural elements that do not differ from the literal language of theclaims, or if they include equivalent structural elements withinsubstantial differences from the literal language of the claims.

What is claimed is:
 1. A joint for coupling a wing tip to a wing base,said joint comprising: a linking member that extends from a first end toa second end, said linking member first end is coupleable to the wingbase, said linking member second end is coupleable to the wing tip, saidlinking member defines a first hinge line and a second hinge line, saidfirst hinge line and said second hinge line are substantially parallel;and at least one actuator, a first end of each said at least oneactuator is coupled to said linking member, a second end of each said atleast one actuator is coupleable to one of the wing base and the wingtip, said at least one actuator is operable to rotate the wing tip aboutsaid first and second hinge lines between a first orientation and asecond orientation relative to the wing base.
 2. The joint according toclaim 1, wherein said first and second hinge lines are offset from eachother by a distance.
 3. The joint according to claim 1, wherein said atleast one actuator cooperates with said linking member such that thesecond orientation defines a rotation from the first orientation aboutsaid first and second hinge lines.
 4. The joint according to claim 1,wherein: each said at least one actuator second end is linearlyextendable relative to said at least one actuator first end; each saidat least one actuator second end is movable to a first position relativeto said at least one actuator first end to position the wing tip in thefirst orientation; and each said at least one actuator second end ismovable to a second position relative to said at least one actuatorfirst end to position the wing tip in the second orientation.
 5. Thejoint according to claim 1, wherein: each said at least one actuatorsecond end is rotatable relative to said at least one actuator first endabout an actuator axis; each said at least one actuator second end ismovable to a first position relative to said at least one actuator firstend to position the wing tip in the first orientation; and each said atleast one actuator second end is movable to a second position relativeto said at least one actuator first end to position the wing tip in thesecond orientation.
 6. The joint according to claim 1, wherein: saidlinking member first end is defined on a first portion of said linkingmember, said linking member first portion comprises a first slot and asecond slot; said linking member second end is defined on a secondportion of said linking member, said linking member second portioncomprises a first pin that defines said first hinge line and a secondpin that defines said second hinge line; and said first slot isconfigured to receive said first pin, said second slot is configured toreceive said second pin.
 7. An aircraft comprising: at least one wingcomprising a wing base and a wing tip; a linking member that extendsfrom a first end to a second end, said linking member first end iscoupled to said wing base, said linking member second end is coupled tosaid wing tip, said linking member defines a first hinge line and asecond hinge line, said first hinge line and said second hinge line aresubstantially parallel; and at least one actuator, a first end of eachsaid at least one actuator is coupled to said linking member, a secondend of each said at least one actuator is coupled to one of said wingbase and said wing tip, said at least one actuator is operable to rotatesaid wing tip about said first and second hinge lines between a firstorientation and a second orientation relative to said wing base.
 8. Theaircraft according to claim 7, wherein said first and second hinge linesare offset from each other by a distance.
 9. The aircraft according toclaim 7, wherein said at least one actuator cooperates with said linkingmember such that the second orientation defines a rotation from thefirst orientation about said first and second hinge lines.
 10. Theaircraft according to claim 7, wherein a flexible outer skin of said atleast one wing extends between said wing base and said wing tip, aportion of said flexible outer skin defined by an inner radius issubstantially smooth when said wing tip is moved between the firstorientation and the second orientation.
 11. The aircraft according toclaim 7, wherein: each said at least one actuator second end is linearlyextendable relative to said at least one actuator first end; each saidat least one actuator second end is movable to a first position relativeto said at least one actuator first end to position the wing tip in thefirst orientation; and each said at least one actuator second end ismovable to a second position relative to said at least one actuatorfirst end to position the wing tip in the second orientation.
 12. Theaircraft according to claim 7, wherein: each said at least one actuatorsecond end is rotatable relative to said at least one actuator first endabout an actuator axis; each said at least one actuator second end ismovable to a first position relative to said at least one actuator firstend to position the wing tip in the first orientation; and each said atleast one actuator second end is movable to a second position relativeto said at least one actuator first end to position the wing tip in thesecond orientation.
 13. The aircraft according to claim 7, wherein: saidlinking member first end is defined on a first portion of said linkingmember, said linking member first portion comprises a first slot and asecond slot; said linking member second end is defined on a secondportion of said linking member, said linking member second portioncomprises a first pin that defines said first hinge line and a secondpin that defines said second hinge line; and said first slot isconfigured to receive said first pin, said second slot is configured toreceive said second pin.
 14. A method of coupling a wing tip and a wingbase, said method comprising: coupling a first end of a linking memberto the wing base; coupling a second end of the linking member to thewing tip, wherein the linking member defines a first hinge line and asecond hinge line, the first hinge line and the second hinge line aresubstantially parallel; coupling a first end of at least one actuator tothe linking member; and coupling a second end of each at least oneactuator to one of the wing base and the wing tip, wherein the at leastone actuator is operable to rotate the wing tip about the first andsecond hinge lines between a first orientation and a second orientationrelative to the wing base.
 15. The method according to claim 14, furthercomprising coupling the second end of the linking member such that thefirst and second hinge lines are offset from each other by a distance.16. The method according to claim 14, further comprising coupling thesecond end of each at least one actuator such that the at least oneactuator cooperates with the linking member such that the secondorientation defines a rotation from the first orientation about thefirst and second hinge lines.
 17. The method according to claim 14,further comprising extending a flexible outer skin between the wing baseand the wing tip, wherein a portion of the flexible outer skin definedby an inner radius is substantially smooth when the wing tip is movedbetween the first orientation and the second orientation.
 18. The methodaccording to claim 14, wherein each at least one actuator second end islinearly extendable relative to the at least one actuator first end,said method further comprises coupling the second end of each at leastone actuator such that: each at least one actuator second end is movableto a first position relative to the at least one actuator first end toposition the wing tip in the first orientation; and each at least oneactuator second end is movable to a second position relative to the atleast one actuator first end to position the wing tip in the secondorientation.
 19. The method according to claim 14, wherein each at leastone actuator second end is rotatable relative to the at least oneactuator first end about an actuator axis, said method further comprisescoupling the second end of each at least one actuator such that: each atleast one actuator second end is movable to a first position relative tothe at least one actuator first end to position the wing tip in thefirst orientation; and each at least one actuator second end is movableto a second position relative to the at least one actuator first end toposition the wing tip in the second orientation.
 20. The methodaccording to claim 14, wherein the linking member first end is definedon a first portion of the linking member and the linking member secondend is defined on a second portion of the linking member, the linkingmember first portion comprises a first slot and a second slot, thelinking member second portion comprises a first pin that defines thefirst hinge line and a second pin that defines the second hinge line,said method further comprises coupling the linking member first portionand the linking member second portion such that the first pin isreceived in the first slot and the second pin is received in the secondslot.